A wing of a large-sized heat-resistant and load-bearing integrated aircraft

Abstract

The present application relates to a large-sized heat-resistant load-bearing integrated aircraft wing, belonging to the technical field of aircraft structures. The large-sized heat-resistant load-bearing integrated aircraft wing includes a fuselage shell. On both sides of the fuselage shell, a first installation groove and a second installation groove are provided. One end of the front wing facing the middle wing is provided with a first groove, and on the middle wing, there is a first lug that is inserted in cooperation with the first groove. One end of the middle wing facing the rear wing is provided with a second groove, and on the rear wing, there is a second lug that is inserted in cooperation with the second groove. The front wing, the middle wing, and the rear wing are connected between the first installation groove and the second installation groove through a front support and a rear support. Heat-resistant putty is arranged at the butt joint between the front wing, the middle wing, and the rear wing; in the present application, through the movable installation of the rear support, the connection structure between it and the fuselage shell can be thermally deformed and matched, avoiding the completely fixed installation method. When the wing generates thermal deformation, it cannot be extended synchronously, resulting in the wing being easily damaged.

Description

Technical Field

[0001] This application relates to the technical field of aircraft structures, and particularly to a large-sized heat-resistant and load-bearing integrated aircraft wing. Background Art

[0002] When a hypersonic aircraft flies at high speed for a long time, the aircraft structure will bear severe aerodynamic heat loads. The wings are exposed to the atmospheric environment and bear the heat loads and force loads of flight. To meet the aerodynamic performance requirements of a high lift-to-drag ratio, the aircraft often adopts large-sized wings to provide sufficient lift. At the same time, to reduce the flight resistance, the wing cross-section thickness is relatively thin. The design of the wing needs to consider factors such as heat loads, force loads, and processability, which is an important part of the aircraft structure design.

[0003] The wings of hypersonic aircraft have the characteristics of large size, thin thickness, harsh heat loads, and large force loads. The wing design is generally divided into two categories: a multi-layer scheme with a heat-insulating outer layer and a load-bearing inner skeleton, and a heat-resistant, heat-insulating, and load-bearing integrated scheme. The outer heat-insulating layer often uses heat-insulating materials with excellent ablation resistance, high temperature resistance, and heat insulation performance. The load-bearing skeleton often uses metal materials with good mechanical properties. However, the multi-layer wing structure has a heavy mass, a large thickness, and a complex structure, and increasingly cannot meet the development needs of aircraft wings. The heat-resistant and load-bearing integrated wings often use metals or composite materials with excellent ablation resistance and high-temperature mechanical properties. For large-sized wings, materials with excellent high-temperature mechanical properties often have a large coefficient of linear expansion, and it is very difficult to design the thermal deformation matching installation between the wings and between the wings and the fuselage at high temperatures.

[0004] In summary, the large-sized wings of aircraft have the characteristics of large size, thin thickness, harsh heat loads, and large force loads. The heat-resistant and load-bearing integrated wings are the development trend, and the thermal deformation matching between the wings and the fuselage is a design difficulty. Summary of the Invention

[0005] An embodiment of this application provides a large-sized heat-resistant and load-bearing integrated aircraft wing to solve the problem that the thermal deformation between the aircraft wing and the fuselage is not easy to match in related technologies.

[0006] An embodiment of this application provides a large-sized heat-resistant and load-bearing integrated aircraft wing, including a body shell, and first installation grooves and second installation grooves are respectively opened on both sides of the body shell;

[0007] Wings, there are two wings, and the two wings are symmetrically arranged on both sides of the body shell. The wings include a front wing, a middle wing, and a rear wing connected in sequence;

[0008] A first groove is opened at one end of the front wing facing the middle wing, a first lug is arranged on the middle wing and is inserted into the first groove in a matching manner, a second groove is opened at one end of the middle wing facing the rear wing, and a second lug is arranged on the rear wing and is inserted into the second groove in a matching manner;

[0009] On one side of the front wing, middle wing, and rear wing facing the body shell, there are front supports and rear supports provided.

[0010] The front wing, middle wing, and rear wing are connected between the first installation groove and the second installation groove through the front supports and rear supports.

[0011] Heat-resistant putty, and the heat-resistant putty is arranged at the butt joint between the front wing, middle wing, and rear wing.

[0012] In some embodiments, there are several of the first installation grooves and the second installation grooves, and they are matched and combined with the front wing, middle wing, and rear wing.

[0013] In some embodiments, the front support of the front wing is installed and connected to the first installation groove through a fixing mechanism.

[0014] The fixing mechanism includes a first pressing plate arranged on the side of the body shell away from the front wing, and the body shell and the front support are fixedly connected through bolts.

[0015] In some embodiments, the outer side of the front support is wrapped with a first heat-insulating block.

[0016] In some embodiments, there is a gap between the second installation groove and the rear support, and the width of the gap is 1.2 times the thermal deformation amount of the wing.

[0017] The rear support of the front wing is connected to the second installation groove through a movable mechanism.

[0018] The movable mechanism includes a transfer plate arranged on the side of the body shell away from the rear support. A waist-shaped hole communicating with the second installation groove is opened on the transfer plate. The width of the waist-shaped hole is matched with the thermal deformation amount of the wing. A second pressing plate is arranged on the side of the transfer plate away from the wing. Bolts are arranged on the second pressing plate and sequentially pass through the second pressing plate and the waist-shaped hole to be bolted to the rear support.

[0019] In some embodiments, the outer side of the rear support is wrapped with a second heat-insulating block.

[0020] In some embodiments, heat-insulating and heat-proof layers are provided between the front wing, middle wing, and rear wing and the body shell.

[0021] Both the first heat-insulating block and the second heat-insulating block are made of quartz ceramic material.

[0022] In some embodiments, the structural principles of the connections between the front wing and the middle wing and the body shell are the same.

[0023] The front support of the rear wing is connected to the first installation groove through a movable mechanism.

[0024] The rear support of the rear wing is connected to the second installation groove through a fixing mechanism.

[0025] In some embodiments, the heat-resistant putty is applied to the surfaces of the first ear and the second ear.

[0026] In some embodiments, the inclined height of the heat-resistant putty on the first ear is the same as the inclined height between the front wing and the middle wing;

[0027] The inclined height of the heat-resistant putty on the second ear is the same as the inclined height between the middle wing and the rear wing.

[0028] The embodiment of the present application provides a large-size heat-resistant and load-bearing integrated aircraft wing. By inserting the first ear of the middle wing into the first groove of the front wing, and then inserting the second ear of the rear wing into the second groove of the middle wing, the front wing, the middle wing and the rear wing can be connected and fixed to each other.

[0029] On the side of the front wing, the middle wing and the rear wing facing the fuselage shell, a front support and a rear support are fixedly connected. The front wing, the middle wing and the rear wing are connected to the fuselage shell by inserting the front support into the first installation groove and inserting the rear support into the second installation groove. Moreover, the front support and the first installation groove are fixedly installed and connected, so that the front support is in a fixed state and cannot move in the first installation groove, while the rear support and the second installation groove are movably installed and connected, so that the rear support can move in the second installation groove. When the wing undergoes thermal deformation and extension, through the movable installation of the rear support, the connection structure between the wing and the fuselage shell can be thermally deformed and matched, avoiding the completely fixed installation method. When the wing generates thermal deformation, it cannot extend synchronously, resulting in the wing being easily damaged, reducing the lifespan and flight efficiency of the aircraft.

[0030] The heat-resistant putty is arranged at the docking part between the front wing, the middle wing and the rear wing. Through the heat-resistant putty, a thermal deformation space is reserved between the front wing and the middle wing and between the middle wing and the rear wing. When the wing is normal, the heat-resistant putty fills the pits between the front wing and the middle wing and between the middle wing and the rear wing to make the wing smooth. When the wing heats up and deforms, the thermal deformation force of the wing can smoothly extrude the putty without affecting the deformation matching of the wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0032] Figure 1 It is a schematic structural diagram provided by the embodiment of the present application;

[0033] Figure 2 Schematic connection diagram provided for the wing in the embodiments of the present application;

[0034] Figure 3 Schematic cross-sectional view provided for the wing in the embodiments of the present application;

[0035] Figure 4 Schematic structural view provided for the wing in the embodiments of the present application;

[0036] Figure 5 Schematic structural view provided for the fixing mechanism in the embodiments of the present application;

[0037] Figure 6 Schematic bottom view provided for the fixing mechanism in the embodiments of the present application;

[0038] Figure 7 Schematic structural view provided for the movable mechanism in the embodiments of the present application;

[0039] Figure 8 Schematic bottom view provided for the movable mechanism in the embodiments of the present application.

[0040] 1. Body housing; 1b. Heat insulation layer; 2. Front wing; 2c. First groove; 3. Middle wing; 3a. Front support; 3b. Rear support; 3c. First lug; 3d. Second groove; 4. Rear wing; 4d. Second lug; 5. Heat-resistant putty; 6. First heat insulation block; 7. First pressing plate; 9. Adapter plate; 10. Second heat insulation block; 12. First installation groove; 13. Second installation groove; 14. Waist-shaped hole; 15. Second pressing plate. Detailed implementation manners

[0041] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Apparently, the described embodiments are some, but not all, of the embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts shall fall within the protection scope of the present application.

[0042] The embodiments of the present application provide a large-size heat-resistant load-bearing integrated aircraft wing, which can solve the problem that it is inconvenient to match the thermal deformation between the aircraft wing and the fuselage.

[0043] See Figure 1-8 As shown, the embodiments of the present application provide a large-size heat-resistant load-bearing integrated aircraft wing, including

[0044] a body housing 1, a wing, and heat-resistant putty 5. The wing is made of a structural material with high temperature resistance, ablation resistance, and good high-temperature mechanical properties, such as high-temperature alloy steel or C / SIC composite material.

[0045] Wherein, first mounting grooves 12 and second mounting grooves 13 are formed on both sides of the body housing 1, and the wings are facilitated to be mounted through the first mounting grooves 12 and the second mounting grooves 13.

[0046] There are two wings, and the two wings are symmetrically arranged on both sides of the body housing 1. The wings include a front wing 2, a middle wing 3 and a rear wing 4 which are connected in sequence. A first groove 2c is formed at one end of the front wing 2 facing the middle wing 3, and a first lug 3c which is matched with the first groove 2c is fixedly connected to one end of the middle wing 3 facing the front wing 2. A second groove 3d is formed at one end of the middle wing 3 facing the rear wing 4, and a second lug 4d which is matched with the second groove 3d is fixedly connected to one end of the rear wing 4 facing the middle wing 3.

[0047] When assembling the wings, first insert the middle wing 3 into the first groove 2c of the front wing 2 through the first lug 3c, and then insert the second lug 4d of the rear wing 4 into the second groove 3d of the middle wing 3, so that the front wing 2, the middle wing 3 and the rear wing 4 can be fixedly connected to each other.

[0048] Front supports 3a and rear supports 3b are fixedly connected to the sides of the front wing 2, the middle wing 3 and the rear wing 4 facing the body housing 1. The front wing 2, the middle wing 3 and the rear wing 4 are connected to the body housing 1 by inserting the front supports 3a into the first mounting grooves 12 and inserting the rear supports 3b into the second mounting grooves 13. The front supports 3a are fixedly installed and connected with the first mounting grooves 12, so that the front supports 3a are fixed and cannot move in the first mounting grooves 12. The rear supports 3b are movably installed and connected with the second mounting grooves 13, so that the rear supports 3b can move in the second mounting grooves 13. When the wings are thermally deformed and extended, through the movable installation of the rear supports 3b, the connection structure between the wings and the body housing 1 can be thermally deformed and matched, avoiding the completely fixed installation method. When the wings generate thermal deformation, they cannot be extended synchronously, resulting in the wings being easily damaged, reducing the service life and flight efficiency of the aircraft.

[0049] Wherein, heat-resistant putty 5 is arranged at the butt joints between the front wing 2, the middle wing 3 and the rear wing 4. Heat deformation spaces are reserved between the front wing 2 and the middle wing 3 and between the middle wing 3 and the rear wing 4 through the heat-resistant putty 5. When the wings are normal, the heat-resistant putty fills the pits between the front wing 2 and the middle wing 3 and between the middle wing 3 and the rear wing 4 to make the wings smooth. When the wings are heated and deformed, the thermal deformation force of the wings can smoothly extrude the putty without affecting the deformation matching of the wings.

[0050] In some alternative embodiments, refer to Figure 1-8As shown in the figure, there are several first mounting grooves 12 and second mounting grooves 13, which are matched and combined with the front wing 2, middle wing 3 and rear wing 4. First mounting grooves 12 and second mounting grooves 13 are provided at the connection between the front wing 2 and the body shell 1, first mounting grooves 12 and second mounting grooves 13 are provided at the connection between the middle wing 3 and the body shell 1, and first mounting grooves 12 and second mounting grooves 13 are provided at the connection between the rear wing 4 and the body shell 1. Through each first mounting groove 12 and second mounting groove 13, the front wing 2, middle wing 3 and rear wing 4 can all be mounted on the body shell 1, and their synchronous thermal deformation matching can be achieved. The installation and connection structural principles of the front wing 2, middle wing 3 and rear wing 4 with the body shell 1 are the same.

[0051] In this embodiment, the front support 3a of the front wing 2 is installed and connected to the first mounting groove 12 through a fixing mechanism. The fixing mechanism includes a first pressing plate 7 provided on the side of the body shell 1 away from the front wing 2, and the body shell 1 and the front support 3a are fixedly connected by bolts.

[0052] The front support 3a of the front wing 2 is inserted into the first mounting groove 12. A first pressing plate 7 is provided on the side of the body shell 1 away from the wing. Since both the first mounting groove 12 and the second mounting groove 13 are through slots in the body shell 1, the first pressing plate 7 is fixedly connected to the side of the body shell 1 away from the wing. The width of the first pressing plate 7 is greater than the width of the first mounting groove 12, so that it can close the first mounting groove 12. Then, bolts are passed through the first pressing plate 7 and bolt-connected to the front support 3a. Through bolt fixation, the front wing 2 and the body shell 1 are fixed, and through the limitation of the first pressing plate 7, the first pressing plate 7 and the front support 3a connected by bolts are mutually clamped, so that the front wing 2 is blocked by the first pressing plate 7 and cannot be pulled out of the first mounting groove 12.

[0053] In this embodiment, the outer side of the front support 3a is wrapped with a first heat insulation block 6. Through the first heat insulation block 6, direct contact between the front support 3a and the body shell 1 is avoided, and heat conduction from the wing to the body shell 1 is reduced.

[0054] In this embodiment, the rear support 3b of the front wing 2 is connected to the second mounting groove 13 through a movable mechanism. The movable mechanism includes a transfer plate 9 provided on the side of the body shell 1 away from the rear support 3b. A waist-shaped hole 14 communicating with the second mounting groove 13 is provided on the transfer plate 9. The width of the waist-shaped hole 14 matches the thermal deformation amount of the wing. A second pressing plate 15 is provided on the side of the transfer plate 9 away from the wing. Bolts are provided on the second pressing plate 15 and sequentially pass through the second pressing plate 15 and the waist-shaped hole 14 to be bolt-connected to the rear support 3b.

[0055] The rear support 3b is inserted into the second installation groove 13. The second installation groove 13 is the same as the first installation groove 12, both being through notches in the body housing 1. A transfer plate 9 is fixedly connected to the side of the body housing 1 away from the rear support 3b. The width of the transfer plate 9 is greater than the width of the second installation groove 13. The second installation groove 13 is closed by the transfer plate 9. A gap is provided between the second installation groove 13 and the rear support 3b, and the width of the gap is 1.2 times the thermal deformation amount of the wing, so that there is enough reserved space for the wing to stretch during thermal deformation. A waist-shaped hole 14 is provided on the transfer plate 9, and the size of the waist-shaped hole 14 matches the thermal deformation amount of the wing. A second pressing plate 15 is provided on the side of the transfer plate 9 away from the wing. Bolts are provided on the second pressing plate 15 that sequentially pass through the second pressing plate 15 and the waist-shaped hole 14 and are bolted to the rear support 3b. The second pressing plate 15 is in a fitting contact with the transfer plate 9 and can slide on the transfer plate 9. The width of the second pressing plate 15 is greater than the width of the waist-shaped hole 14 to prevent the second pressing plate 15 from extending into the waist-shaped hole 14 and preventing the wing from moving. When the wing undergoes thermal deformation and stretches, since there is a reserved deformation space in the second installation groove 13, the stretching of the wing will drive the bolts to move in the second installation groove 13 at this time. While the bolts are moving, the second pressing plate 15 will move, enabling the wing to stretch during thermal deformation and preventing damage caused by the inability to stretch when the wing undergoes thermal deformation and stretches.

[0056] In this embodiment, a second heat insulation block 10 is included on the outer side of the rear support 3b. By means of the second heat insulation block 10, direct contact between the rear support 3b and the body housing 1 is avoided, reducing the heat conduction from the wing to the body housing 1.

[0057] In this embodiment, heat insulation layers 1b are provided on the contact surfaces between the front wing 2, the middle wing 3, and the rear wing 4 and the body housing 1. By means of the heat insulation layers 1b, direct contact between the wing and the body housing 1 is avoided, reducing the heat conduction on the contact surfaces between the wing and the body housing 1.

[0058] Both the first heat insulation block 6 and the second heat insulation block 10 are made of quartz ceramic material. Quartz ceramic has high temperature resistance, low thermal conductivity, stable structure at high temperatures, and sufficient mechanical properties.

[0059] In this embodiment, the structural principles of the connections between the front wing 2 and the middle wing 3 and the body housing 1 are the same.

[0060] The front support 3a of the rear wing 4 is connected to the first installation groove 12 through a movable mechanism, and the rear support 3b of the rear wing 4 is connected to the second installation groove 13 through a fixed mechanism.

[0061] The front wing 2 and the front end of the middle wing 3 are fixedly installed, and the rear end is axially slidably installed. The rear end of the rear wing 4 is fixedly installed, and the front end is axially slidably installed. After installation, the front wing 2 and the middle wing 3 deform and elongate backward after temperature rise, and the rear wing 4 deforms and elongates forward after temperature rise. Through the structural principle of deforming and stretching from both ends to the middle, the connection between the wings is more stable and stronger.

[0062] In some alternative embodiments, as shown in Figure 3 Heat-resistant putty 5 is also applied to the surfaces of the first ear 3c and the second ear 4d. To meet the requirements of the aerodynamic shape and avoid pits at the docking part of the front wing 2 and the middle wing 3, heat-resistant putty 5 is applied to the inserted pits, so that there are no gaps or pits in the lap between the front wing 2, the middle wing 3 and the rear wing 4 when the wings have no thermal deformation, and its surface is smooth. Since the first ear 3c and the second ear 4d are not completely inserted into the first groove 2c and the second groove 3d, when the wings have thermal deformation, the wings will move towards the extended shape through the rear support 3b. The first groove 2c and the second groove 3d will move towards the direction of the first ear 3c and the second ear 4d during thermal deformation. During the movement, part of the heat-resistant putty 5 will be extruded. The heat-resistant putty 5 that is not extruded still blocks the pit, making the surface of the wing smooth and complete until the maximum thermal deformation amount is reached, and then all the heat-resistant putty 5 can be extruded. At the same time, the first ear 3c and the second ear 4d will also be completely inserted into the first groove 2c and the second groove 3d, so that there are no gaps or pits between the front wing 2, the middle wing 3 and the rear wing 4, and the surface of the wing remains smooth.

[0063] In this embodiment, the inclined height of the heat-resistant putty 5 on the first ear 3c is the same as the inclined height between the front wing 2 and the middle wing 3, and the inclined height of the heat-resistant putty 5 on the second ear 4d is the same as the inclined height between the middle wing 3 and the rear wing 4, so that the heat-resistant putty 5 maintains the same inclined height as the wing, maintaining the integrity of the fluid streamline of the wing.

[0064] The working principle and process of this application:

[0065] When the body starts to undergo thermal deformation, the rear supports 3b on the front wing 2, middle wing 3, and rear wing 4 drive the bolts to move within the second installation groove 13 through the stretching movement caused by thermal deformation, enabling the wings to stretch during thermal deformation, thus avoiding damage caused by the inability to stretch when the wings thermally deform and extend. At the same time, the first lug 3c and the second lug 4d are not completely inserted into the first groove 2c and the second groove 3d. Therefore, when the wings undergo thermal deformation, the rear supports 3b of the front wing 2 and the middle wing 3 will stretch and move, the first groove 2c and the second groove 3d will move towards the direction of the first lug 3c and the second lug 4d during thermal deformation, and the second lug 4d of the rear wing 4 will move towards the direction of the second groove 3d. During the movement, part of the heat-resistant putty 5 will be extruded, and the heat-resistant putty 5 that is not extruded still blocks the pits, making the surface of the wings smooth and complete. Until the maximum thermal deformation amount is reached, all the heat-resistant putty 5 can be extruded. At the same time, the first lug 3c and the second lug 4d will also be completely inserted into the first groove 2c and the second groove 3d, ensuring that there are no gaps or pits between the front wing 2, middle wing 3, and rear wing 4, and still keeping the surface of the wings smooth.

[0066] In the description of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "upper" and "lower" is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0067] It should be noted that in the present application, relative terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise", or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or device including a series of elements not only includes those elements but also includes other elements not explicitly listed, or further includes elements inherent to such a process, method, article, or device. Without further limitation, an element defined by the statement "including one..." does not exclude the existence of another identical element in the process, method, article, or device including the said element.

[0068] The above are only specific embodiments of the present application, enabling those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to these embodiments shown herein, but rather will be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A wing of a large-sized heat-resistant and load-bearing integrated aircraft, characterized in that, Comprising: An airframe housing (1), on both sides of which are provided with a first mounting groove (12) and a second mounting groove (13); Wings, there are two wings, which are symmetrically arranged on both sides of the airframe housing (1), and each wing comprises a front wing (2), a middle wing (3) and a rear wing (4) connected in sequence; One end of the front wing (2) facing the middle wing (3) is provided with a first groove (2c), on the middle wing (3) is provided with a first lug (3c) that fits and inserts into the first groove (2c), one end of the middle wing (3) facing the rear wing (4) is provided with a second groove (3d), and on the rear wing (4) is provided with a second lug (4d) that fits and inserts into the second groove (3d); On the side of the front wing (2), middle wing (3) and rear wing (4) facing the airframe housing (1), there are provided a front support (3a) and a rear support (3b); The front wing (2), middle wing (3) and rear wing (4) are connected between the first mounting groove (12) and the second mounting groove (13) through the front support (3a) and the rear support (3b); Heat-resistant putty (5), which is arranged at the docking part between the front wing (2), middle wing (3) and rear wing (4); There are several of the first mounting groove (12) and the second mounting groove (13), and they are matched and combined with the front wing (2), middle wing (3) and rear wing (4); the front support (3a) of the front wing (2) is installed and connected with the first mounting groove (12) through a fixing mechanism; The fixing mechanism includes a first pressing plate (7) arranged on the side of the airframe housing (1) away from the front wing (2), and the airframe housing (1) and the front support (3a) are fixedly connected by bolts; There is a gap between the second mounting groove (13) and the rear support (3b), and the width of the gap is 1.2 times the thermal deformation amount of the wing; The rear support (3b) of the front wing (2) is connected with the second mounting groove (13) through a movable mechanism; The movable mechanism includes a transfer plate (9) arranged on the side of the airframe housing (1) away from the rear support (3b), on the transfer plate (9) is provided with a waist-shaped hole (14) communicating with the second mounting groove (13), the width of the waist-shaped hole (14) matches the thermal deformation amount of the wing, on the side of the transfer plate (9) away from the wing is provided with a second pressing plate (15), and on the second pressing plate (15) is provided with a bolt that sequentially passes through the second pressing plate (15) and the waist-shaped hole (14) and is bolted to the rear support (3b); 2. The wing of a large-size heat-resistant load-bearing integrated aircraft as claimed in claim 1, wherein: The outer side of the front support (3a) is wrapped with a first heat-insulating block (6).

3. The wing of a large-size heat-resistant load-bearing integrated aircraft as claimed in claim 2, wherein: The outer side of the rear support (3b) is wrapped with a second heat-insulating block (10).

4. The wing of a large-size heat-resistant load-bearing integrated aircraft as claimed in claim 3, wherein: An anti-heat-insulating layer (1b) is provided between the front wing (2), middle wing (3), rear wing (4) and the airframe housing (1); Both the first heat insulation block (6) and the second heat insulation block (10) are made of quartz ceramic material.

5. The large-size heat-proof and load-bearing integrated aircraft wing according to any one of claims 1-4, characterized in that: The structural principles of the connections between the front wing (2) and the middle wing (3) and the fuselage shell (1) are the same; A movable mechanism is provided for connecting the front support (3a) of the rear wing (4) and the first installation groove (12); A fixing mechanism is provided for connecting the rear support (3b) of the rear wing (4) and the second installation groove (13).

6. The large-size heat-proof and load-bearing integrated aircraft wing according to claim 1, characterized in that: The heat-proof putty (5) is applied to the surfaces of the first ear (3c) and the second ear (4d).

7. The large-size heat-proof and load-bearing integrated aircraft wing according to claim 6, characterized in that: The inclined height of the heat-proof putty (5) on the first ear (3c) is the same as the inclined height between the front wing (2) and the middle wing (3); The inclined height of the heat-proof putty (5) on the second ear (4d) is the same as the inclined height between the middle wing (3) and the rear wing (4).

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